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Shock/boundary' layer interaction often exists in hypersonic inlets. Thus, a new method based on deformable bump to control boundary layer separation is brought forward in this paper. Computational results indicate that the method is effective to control shock/boundary-layer interaction by means of the precompression effect at windward side of the bump, the weakening effect on reflected shock and the accelerating effect on the boundary layer flow of expansion wave. When the shock impingement position is near the expansion wave-generated area at leeward side of the bump, the size of the separation bubble is greatly reduced. Furthermore, the control effect can be enhanced by increasing the bump height within the proper range. However, excessive height of the bump can strengthen the induced compression and expansion waves thus bringing negative effect on the inlet. In addition, the curvature of concave region at the bump windward side should be small and the largest curvature point in the expansion wave-generated area should be close to the shock impingement position while the curvatures of concave and prominent regions at the bump leeward side should be approximately equal. [ABSTRACT FROM AUTHOR]